Method and device for reducing the increase in temperature at the surface of the terrestrial globe, vehicle and station for implementing said method

Abstract

Disclosed is a method for reducing the increase in temperature at the surface of the earth and the increase in the content of carbon dioxide in the atmosphere due to the fossil fuel and non-fossil fuel combustion operations, remarkable in that it consists in reducing the increase in the temperature of the earth and the increase in the content of carbon dioxide in the atmosphere, which reductions in the temperature of the earth and of the content of carbon dioxide are achieved by reducing the drop in the oxygen content in the atmosphere, which reduction in the drop in the oxygen content includes: producing pure oxygen or producing hydrogen peroxide, and using for fuel combustion the oxygen or hydrogen peroxide to reduce the consumption of oxygen contained in the air during the combustion operations. Also disclosed is the device, the vehicle and the plant for carrying out the method.

1 . An engine for propulsion of an aircraft, the engine enabling a reduction in an increase in the temperature of the air of the atmosphere and the temperature of the water of the oceans and seas of the Earth, the engine comprising:
 a combustion chamber (C 1 ) containing fossil or non-fossil fuel, use of which fuel generates, by consumption of oxygen from atmospheric air or by consumption of oxygen from atmospheric air enriched with pure oxygen or by consumption of pure oxygen, a gas containing heat and water vapor, the combustion chamber having an inlet (E 1 );   a propeller (H 1 );   a tank (R 1 ) connected to the combustion chamber (C 1 );   a fuel pump (P 1 );   at least one fuel shut-off and adjustment valve (V); and   an ambient air inlet equipped with a shut-off and adjustment valve,   the combustion chamber C 1 :   using the fossil or non-fossil fuel from the tank (R 1 ) arriving in the combustion chamber via inlet (E 1 ),   generating by consumption of oxygen from atmospheric air or by consumption of oxygen from atmospheric air enriched with pure oxygen or by consumption of pure oxygen, entering the combustion chamber through the inlet (E 2 ), a combustion gas leaving the combustion chamber through outlet S 1  and containing heat, sensible heat and latent heat, and water vapor, which water vapor has a triple effect on increasing the temperature of the air of the atmosphere and the temperature of the water of the oceans and seas of the Earth by:   direct heating of the air of the Earth's atmosphere from latent heat in the vapor,   indirect heating of the Earth's atmosphere by the greenhouse effect by absorption of infrared radiation emitted by the Earth's surface of water vapor,   increase in the temperature of the water of the oceans and seas on the surface of the Earth by reducing the blocking of evaporation of the water of the oceans and seas on the surface of the Earth, which reduction of evaporation is done by decreasing the concentration gradient of water vapor between the surface of the water of the seas and oceans and the atmospheric air above the water; and   a heat exchanger (X 1 ) with ambient air condensation (A 1 )-combustion gas or ambient air condensation (A 1 )-liquid-combustion gas or liquid-combustion gas condensation, which heat exchanger removes heat contained in the combustion gas and the condensation of water vapor in the form of liquid water.   
     
     
         2 . The engine according to  claim 1 , further comprising a pure oxygen tank (R 2 ), the pure oxygen tank having an outlet with a shut-off and adjustment valve connected to a second inlet (E 2 ) of the combustion chamber (C 1 ) via a pipe. 
     
     
         3 . The engine according to  claim 2 , further comprising a recycling circuit (Y 1 ) of the combustion gas after extraction of the heat and condensation of the water vapor, which recycling circuit is provided with a shut-off and adjustment valve connected to the second inlet (E 2 ) of the combustion chamber via a pipe. 
     
     
         4 . The engine according to  claim 3 , further comprising a mixer/selector, which mixer/selector is provided with an inlet (E 3 ) for ambient air (A 1 ), the inlet (E 3 ) for ambient air (A 1 ) being equipped with a shut-off and adjustment valve, an inlet for pure oxygen and an inlet for the combustion gas recycled after extraction of the heat and condensation of the water vapor. 
     
     
         5 . The engine according to  claim 1 , further comprising an exhaust circuit into the air of the combustion gas after combustion gas cooling and the condensation of the water vapor, which exhaust circuit is connected to the outlet of the condensation heat exchanger and comprises a shut-off and adjustment valve and an outlet (S 2 ). 
     
     
         6 . The engine according to  claim 5 , wherein a reheated cooling liquid after having been used to cool the combustion gas and to condense the water vapor in the heat exchanger (X 1 ) with ambient air (A 1 )-liquid-combustion gas condensation or with liquid-combustion gas condensation is recovered for use on the aircraft from the reheated cooling liquid itself. 
     
     
         7 . The engine according to  claim 1 , further comprising a storage tank for condensed water. 
     
     
         8 . The engine according to  claim 1 , further comprising a storage tank for condensed water, the water stored in the storage tank being treated to use on the aircraft. 
     
     
         9 . The engine according to  claim 2 , wherein the oxygen stored in the pure oxygen tank (R 2 ) is in liquid form. 
     
     
         10 . The engine according to  claim 2 , wherein the oxygen stored in the pure oxygen tank (R 2 ) is in the form of hydrogen peroxide with a mass concentration of hydrogen peroxide of between 30 and 70%. 
     
     
         11 . The engine according to  claim 2 , wherein,
 the oxygen stored in the pure oxygen tank (R 2 ) is in the form of hydrogen peroxide with a mass concentration of hydrogen peroxide of between 30 and 70%, and   the hydrogen peroxide is decomposed by catalytic or electrocatalytic or electrical decomposition in the form of gaseous oxygen before use.   
     
     
         12 . The engine for the propulsion of an aircraft according to  claim 1 , wherein the combustion chamber (C 1 ) is a fuel cell. 
     
     
         13 . The engine according to  claim 1 , wherein the engine is a hydrogen turbojet. 
     
     
         14 . The engine according to  claim 1 , wherein the fuel contained in the tank (R 1 ) is a cryogenic liquid fuel, fossil or non-fossil. 
     
     
         15 . The engine according to  claim 1 , wherein the fuel contained in the tank (R 1 ) is liquid hydrogen. 
     
     
         16 . The engine according to  claim 1 , wherein a heated cooling liquid used to cool the combustion gas and to condense the water vapor in the heat exchanger (X 1 ) with ambient air (A 1 )-liquid-combustion gas condensation or with liquid-combustion gas condensation is the cryogenic liquid fuel contained in the tank (R 1 ). 
     
     
         17 . The engine according to  claim 1 , further comprising one or more of the heat exchanger (X 1 ) with ambient air (A 1 )-liquid-combustion gas condensation or with ambient air (A 1 )-combustion gas condensation and one or more compression means for liquefying at low pressure, less than 30 bar, and low temperature, temperature below −20° C., the carbon dioxide contained in the combustion gas resulting from the use of fossil fuels and when the aircraft is at an altitude where the temperature of the ambient air (A 1 ) is between −20 and −50° C., after cooling of the combustion gases and condensation of the water vapor. 
     
     
         18 . The engine according to  claim 1 , further comprising one or more tanks for storing liquefied carbon dioxide. 
     
     
         19 . The engine according to  claim 1 , further comprising: plural of the heat exchanger (X 1 ) with ambient air (A 1 )-liquid-combustion gas condensation or with ambient air (A 1 )-combustion gas condensation and plural compression means for liquefying at low pressure, less than 30 bar, and low temperature, temperature below −20° C., the carbon dioxide contained in the combustion gas resulting from the use of fossil fuels and when the aircraft is at an altitude where the temperature of the ambient air (A 1 ) is between −20 and −50° C., after cooling of the combustion gases and condensation of the water vapor.